Two families of airfoil sections which can be used for helicopter/rotorcraft rotor blades or aircraft propellers of a particular shape are prepared. An airfoil of either family is one which could be produced by the combination of a camber line and a thickness distribution or a thickness distribution which is scaled from these. An airfoil of either family has a unique and improved aerodynamic performance. The airfoils of either family are intended for use as inboard sections of a helicopter rotor blade or an aircraft propeller. The novelty appears to reside in the specific shapes of the airfoil profiles which simultaneously permit high maximum lift coefficients at Mach numbers up to 0.50, low pitching moment coefficients about the quarter chord for lift coefficients from -0.2 to 1.0 at Mach numbers up to 0.63, and high drag divergence Mach numbers at lift coefficients from 0.0 to 0.30.
High Lift, Low Pitching Moment Airfoils
1986
30 pages
Report
Keine Angabe
Englisch
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